(Dicke 12.28%) (e171-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: (Dicke 12.28%) (e171-il) Reynolds number: 200,000 Max Cl/Cd: 47.81 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e171-il-200000-n5.txt Download as CSV file: xf-e171-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: (Dicke 12.28%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8164 0.09117 0.08733 -0.0142 1.0000 0.0088
-13.750 -0.8477 0.08043 0.07634 -0.0210 1.0000 0.0086
-13.500 -0.8678 0.07315 0.06889 -0.0254 1.0000 0.0086
-13.250 -0.8865 0.06674 0.06226 -0.0289 1.0000 0.0086
-13.000 -0.9007 0.06153 0.05686 -0.0314 1.0000 0.0087
-12.750 -0.9145 0.05667 0.05179 -0.0333 1.0000 0.0087
-12.500 -0.9247 0.05259 0.04751 -0.0344 1.0000 0.0087
-12.250 -0.9329 0.04899 0.04371 -0.0349 1.0000 0.0088
-12.000 -0.9388 0.04584 0.04038 -0.0350 1.0000 0.0090
-11.750 -0.9421 0.04307 0.03742 -0.0345 1.0000 0.0091
-11.500 -0.9440 0.04058 0.03475 -0.0337 1.0000 0.0094
-11.250 -0.9438 0.03820 0.03215 -0.0326 1.0000 0.0094
-11.000 -0.9416 0.03615 0.02988 -0.0311 1.0000 0.0098
-10.750 -0.9375 0.03423 0.02778 -0.0294 1.0000 0.0101
-10.500 -0.9315 0.03249 0.02585 -0.0276 1.0000 0.0104
-10.250 -0.9242 0.03084 0.02403 -0.0256 1.0000 0.0108
-10.000 -0.9154 0.02945 0.02247 -0.0235 1.0000 0.0115
-9.750 -0.9031 0.02858 0.02141 -0.0216 1.0000 0.0123
-9.500 -0.8956 0.02684 0.01960 -0.0194 1.0000 0.0131
-9.250 -0.8837 0.02569 0.01841 -0.0177 1.0000 0.0141
-9.000 -0.8706 0.02455 0.01718 -0.0159 1.0000 0.0149
-8.750 -0.8569 0.02345 0.01597 -0.0141 1.0000 0.0160
-8.500 -0.8424 0.02243 0.01483 -0.0123 1.0000 0.0172
-8.250 -0.8295 0.02130 0.01358 -0.0103 1.0000 0.0186
-8.000 -0.8141 0.02042 0.01268 -0.0088 1.0000 0.0211
-7.750 -0.7964 0.01974 0.01192 -0.0073 1.0000 0.0241
-7.500 -0.7810 0.01885 0.01097 -0.0055 1.0000 0.0270
-7.250 -0.7640 0.01814 0.01024 -0.0040 1.0000 0.0316
-7.000 -0.7465 0.01747 0.00951 -0.0023 1.0000 0.0365
-6.750 -0.7298 0.01676 0.00881 -0.0006 1.0000 0.0438
-6.500 -0.7130 0.01609 0.00815 0.0011 1.0000 0.0562
-6.250 -0.6964 0.01542 0.00758 0.0028 1.0000 0.0747
-6.000 -0.6741 0.01478 0.00703 0.0032 0.9965 0.0992
-5.750 -0.6410 0.01406 0.00645 0.0014 0.9837 0.1358
-5.500 -0.6101 0.01326 0.00589 -0.0001 0.9673 0.1889
-5.250 -0.5809 0.01232 0.00534 -0.0013 0.9477 0.2695
-5.000 -0.5502 0.01152 0.00487 -0.0026 0.9290 0.3526
-4.750 -0.5181 0.01106 0.00460 -0.0037 0.9105 0.4157
-4.500 -0.4873 0.01081 0.00441 -0.0044 0.8915 0.4607
-4.250 -0.4582 0.01067 0.00427 -0.0046 0.8729 0.4960
-4.000 -0.4302 0.01060 0.00414 -0.0044 0.8556 0.5201
-3.750 -0.4032 0.01055 0.00399 -0.0041 0.8393 0.5389
-3.500 -0.3767 0.01053 0.00387 -0.0037 0.8243 0.5553
-3.250 -0.3502 0.01050 0.00376 -0.0033 0.8106 0.5697
-3.000 -0.3238 0.01049 0.00367 -0.0029 0.7981 0.5822
-2.750 -0.2973 0.01047 0.00356 -0.0025 0.7862 0.5940
-2.500 -0.2707 0.01045 0.00348 -0.0021 0.7749 0.6051
-2.250 -0.2440 0.01044 0.00340 -0.0018 0.7646 0.6157
-2.000 -0.2172 0.01043 0.00331 -0.0015 0.7551 0.6253
-1.750 -0.1903 0.01041 0.00326 -0.0012 0.7455 0.6341
-1.500 -0.1633 0.01040 0.00319 -0.0010 0.7366 0.6435
-1.250 -0.1363 0.01039 0.00315 -0.0008 0.7285 0.6520
-1.000 -0.1091 0.01037 0.00311 -0.0006 0.7198 0.6600
-0.750 -0.0820 0.01037 0.00307 -0.0004 0.7125 0.6679
-0.500 -0.0546 0.01036 0.00305 -0.0003 0.7042 0.6749
-0.250 -0.0273 0.01036 0.00303 -0.0001 0.6973 0.6825
0.000 0.0000 0.01035 0.00303 0.0000 0.6894 0.6894
0.250 0.0273 0.01036 0.00303 0.0001 0.6825 0.6972
0.500 0.0546 0.01036 0.00305 0.0003 0.6749 0.7042
0.750 0.0819 0.01037 0.00307 0.0004 0.6679 0.7125
1.000 0.1091 0.01037 0.00311 0.0006 0.6600 0.7198
1.250 0.1363 0.01039 0.00315 0.0008 0.6520 0.7285
1.500 0.1633 0.01040 0.00319 0.0010 0.6435 0.7366
1.750 0.1903 0.01041 0.00326 0.0012 0.6341 0.7454
2.000 0.2172 0.01043 0.00332 0.0015 0.6253 0.7551
2.250 0.2440 0.01044 0.00340 0.0018 0.6157 0.7646
2.500 0.2708 0.01045 0.00348 0.0021 0.6052 0.7749
2.750 0.2973 0.01047 0.00356 0.0025 0.5940 0.7862
3.000 0.3238 0.01049 0.00367 0.0029 0.5824 0.7981
3.250 0.3502 0.01050 0.00376 0.0033 0.5697 0.8106
3.500 0.3767 0.01053 0.00387 0.0037 0.5554 0.8243
3.750 0.4033 0.01055 0.00399 0.0041 0.5389 0.8393
4.000 0.4302 0.01060 0.00414 0.0044 0.5199 0.8556
4.250 0.4582 0.01067 0.00427 0.0046 0.4959 0.8729
4.500 0.4873 0.01081 0.00441 0.0044 0.4607 0.8914
4.750 0.5181 0.01106 0.00460 0.0037 0.4155 0.9106
5.000 0.5503 0.01151 0.00487 0.0026 0.3534 0.9291
5.250 0.5809 0.01232 0.00534 0.0013 0.2694 0.9479
5.500 0.6101 0.01326 0.00589 0.0001 0.1892 0.9675
5.750 0.6411 0.01406 0.00645 -0.0014 0.1358 0.9839
6.000 0.6743 0.01478 0.00703 -0.0033 0.0993 0.9967
6.250 0.6961 0.01543 0.00758 -0.0027 0.0744 1.0000
6.500 0.7128 0.01609 0.00815 -0.0010 0.0566 1.0000
6.750 0.7297 0.01676 0.00880 0.0006 0.0439 1.0000
7.000 0.7465 0.01747 0.00951 0.0024 0.0365 1.0000
7.250 0.7640 0.01813 0.01024 0.0040 0.0315 1.0000
7.500 0.7811 0.01885 0.01097 0.0055 0.0269 1.0000
7.750 0.7966 0.01973 0.01191 0.0073 0.0240 1.0000
8.000 0.8143 0.02042 0.01268 0.0087 0.0212 1.0000
8.250 0.8300 0.02128 0.01356 0.0103 0.0186 1.0000
8.500 0.8428 0.02243 0.01483 0.0123 0.0172 1.0000
8.750 0.8573 0.02345 0.01598 0.0140 0.0160 1.0000
9.000 0.8711 0.02455 0.01718 0.0158 0.0148 1.0000
9.250 0.8842 0.02570 0.01841 0.0176 0.0140 1.0000
9.500 0.8963 0.02685 0.01963 0.0193 0.0131 1.0000
9.750 0.9040 0.02855 0.02139 0.0215 0.0123 1.0000
10.000 0.9153 0.02970 0.02270 0.0234 0.0118 1.0000
10.250 0.9251 0.03085 0.02404 0.0254 0.0108 1.0000
10.500 0.9324 0.03249 0.02586 0.0274 0.0104 1.0000
10.750 0.9384 0.03429 0.02784 0.0293 0.0101 1.0000
11.000 0.9425 0.03618 0.02992 0.0309 0.0097 1.0000
11.250 0.9445 0.03829 0.03226 0.0324 0.0095 1.0000
11.500 0.9450 0.04053 0.03468 0.0336 0.0092 1.0000
11.750 0.9433 0.04311 0.03747 0.0344 0.0091 1.0000
12.000 0.9393 0.04590 0.04044 0.0348 0.0089 1.0000
12.250 0.9341 0.04897 0.04368 0.0347 0.0088 1.0000
12.500 0.9265 0.05248 0.04738 0.0341 0.0086 1.0000
12.750 0.9145 0.05689 0.05203 0.0330 0.0087 1.0000
13.000 0.9028 0.06143 0.05676 0.0312 0.0087 1.0000
13.250 0.8877 0.06677 0.06228 0.0287 0.0086 1.0000
13.500 0.8686 0.07330 0.06903 0.0251 0.0086 1.0000
13.750 0.8432 0.08171 0.07769 0.0200 0.0088 1.0000
14.000 0.8111 0.09285 0.08906 0.0129 0.0090 1.0000
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Polar data table (+)
Polar graphs
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